Dynamics Simulation and Analysis of Transition Stage of Tilt-Rotor Aircraft

2016 ◽  
Vol 842 ◽  
pp. 251-258 ◽  
Author(s):  
Muhammad Rafi Hadytama ◽  
Rianto A. Sasongko
Keyword(s):  
Dynamic Response ◽  
Equations Of Motion ◽  
Flight Dynamics ◽  
Dynamics Simulation ◽  
Tilt Rotor ◽  
Vertical Takeoff And Landing ◽  
Improved Stability ◽  
Simulation Results ◽  
Vtol Aircraft ◽  
Vertical Takeoff

This paper presents the flight dynamics simulation and analysis of a tilt-rotor vertical takeoff and landing (VTOL) aircraft on transition phase, that is conversion from vertical or hover to horizontal or level flight and vice versa. The model of the aircraft is derived from simplified equations of motion comprising the forces and moments working on the aircraft in the airplane's longitudinal plane of motion. This study focuses on the problem of the airplane's dynamic response during conversion phase, which gives an understanding about the flight characteristics of the vehicle. The understanding about the flight dynamics characteristics is important for the control system design phase. Some simulation results are given to provide better visualization about the behaviour of the tilt-rotor. The simulation results show that both transition phases are quite stable, although an improved stability can give better manoeuver and attitude handling. Improvement on the simulation model is also required to provide more accurate and realistic dynamic response of the vehicle.

Military Vertical Takeoff and Landing (VTOL) Propulsion Systems Design

1972 ◽  
Author(s):  
A. O. Kohn
Keyword(s):  
Low Power ◽  
Systems Design ◽  
Propulsion Systems ◽  
Vertical Takeoff And Landing ◽  
Power Setting ◽  
Vtol Aircraft ◽  
Vertical Takeoff ◽  
Engine Size ◽  
Maximum Thrust ◽  
Selection Of

This paper deals with the parameters that must be considered in the selection and design of propulsion systems for military VTOL aircraft. Some of these parameters, for instance lightweight, are applicable to engines for all types of aircraft. For the VTOL aircraft, special emphasis must be placed on many of these parameters since aircraft takeoff gross weight determines engine size. Other significant considerations in the selection of the propulsion system include: (a) the ratio of subsonic cruise thrust to maximum thrust; and, (b) exhaust downwash characteristics. Consideration (a) is important because, in the case where no auxiliary lift engines or devices are used, subsonic cruise thrust is about 25 to 30 percent maximum, and at this low power setting, specific fuel consumption is increasing rapidly. Exhaust downwash characteristics are significant because of the variety of landing and takeoff sites likely to be encountered (i.e., shipboard or unprepared fields).

scholarly journals Performance Metrics Required of Next-Generation Batteries to Electrify Vertical Takeoff and Landing (VTOL) Aircraft

2018 ◽  
Vol 3 (12) ◽  
pp. 2989-2994 ◽  
Author(s):  
William L. Fredericks ◽  
Shashank Sripad ◽  
Geoffrey C. Bower ◽  
Venkatasubramanian Viswanathan
Keyword(s):  
Performance Metrics ◽  
Next Generation ◽  
Vertical Takeoff And Landing ◽  
Vtol Aircraft ◽  
Vertical Takeoff

Aircraft/Deck Interface Dynamics for Destroyers

1987 ◽  
Vol 24 (01) ◽  
pp. 15-25
Author(s):  
Peter J. F. O'Reilly
Keyword(s):  
Dynamic Analysis ◽  
Research Program ◽  
Interface Dynamics ◽  
Analytical Technique ◽  
Aircraft Landing ◽  
Vertical Takeoff And Landing ◽  
Time Histories ◽  
Vtol Aircraft ◽  
Vertical Takeoff

The interface between vertical takeoff and landing (VTOL) aircraft and destroyer and frigate-type warships involves a great many factors. This paper discusses a computer analytical technique which permits dynamic analysis of the aircraft landing or taking off from a moving deck or being handled or stowed on the ship. A condensed explanation of how the synthetic time histories are generated is contained in the Appendix. Two examples of how the technique has been used are included: first, a Recovery Assist and Secure System (RAS) analysis, and second, a pilot landing aid system, the Landing Period Designator (LPD) research program.

scholarly journals Structural Design and Dynamics Simulation Analysis of A Certain Type of Co-frame Launcher

2021 ◽  
Vol 2125 (1) ◽  
pp. 012037
Author(s):  
Hanchao Liu ◽  
Anxin Guo ◽  
Xuezhi Wang
Keyword(s):  
Dynamic Response ◽  
3D Modeling ◽  
Structural Design ◽  
Simulation Analysis ◽  
Dynamics Simulation ◽  
Dynamic Parameters ◽  
Dynamics Model ◽  
Modeling Software ◽  
Design Requirements ◽  
Simulation Results

Abstract To study the dynamic response of a certain type of co-frame launcher during launch, this article uses the 3D modeling software Pro/E to import the model into Adams from the perspective of launch dynamics. the launch dynamics model of the shared-frame launcher is established. We apply the ejection thrust of the two types of missiles to the corresponding ejection devices and measure and collect the dynamic parameters of the cartridge system. The simulation results show that the dynamic parameters of the A and B missiles are in line with the available overload design requirements. The B-type missiles are superior to the A-type missiles in terms of ballistic orbit contact force and ejection attitude.

scholarly journals PID vs LQR controller for tilt rotor airplane

2020 ◽  
Vol 10 (6) ◽  
pp. 6309
Author(s):  
Aoued Houari ◽  
Imine Bachir ◽  
Della Krachai Mohame ◽  
Mohamed Kara Mohamed
Keyword(s):  
Degrees Of Freedom ◽  
Feasible Solution ◽  
Pid Controllers ◽  
Rotor Speed ◽  
Huge Number ◽  
Combination Technique ◽  
Tilt Rotor ◽  
Vertical Takeoff And Landing ◽  
Lqr Controller ◽  
Vertical Takeoff

The main thematic of this paper is controlling the main manoeuvers of a tilt rotor UAV airplane in several modes such as vertical takeoff and landing, longitudinal translation and the most important phase which deal with the transition from the helicopter mode to the airplane mode and visversa based on a new actuators combination technique for specially the yaw motion with not referring to rotor speed control strategy which is used in controlling the attitude of a huge number of vehicles nowadays. This new actuator combination is inspired from that the transient response of a trirotor using tilting motion dynamics provides a faster response than using rotor speed dynamics. In the literature, a lot of control technics are used for stabilizing and guarantee the necessary manoeuvers for executing such task, a multiple Attitude and Altitude PID controllers were chosen for a simple linear model of our tilt rotor airplane in order to fulfill the desired trajectory, for reasons of complexity of our model the multiple PID controller doesnt take into consideration all the coupling that exists between the degrees of freedom in our model, so an LQR controller is adopted for more feasible solution of complex manoeuvering, the both controllers need linearization of the model for an easy implementation.

scholarly journals Challenges and key requirements of batteries for electric vertical takeoff and landing aircraft

Joule ◽  
2021 ◽  
Author(s):  
Xiao-Guang Yang ◽  
Teng Liu ◽  
Shanhai Ge ◽  
Eric Rountree ◽  
Chao-Yang Wang
Keyword(s):  
Vertical Takeoff And Landing ◽  
Vertical Takeoff

Study on Engine Kinematics and Dynamics Simulation Based on COSMOSMotion

2012 ◽  
Vol 503-504 ◽  
pp. 731-734
Author(s):  
Xiao Xu Liu ◽  
Min Chen ◽  
Ai Hua Tang
Keyword(s):  
Virtual Prototype ◽  
Dynamics Simulation ◽  
Kinematics And Dynamics ◽  
Engine Model ◽  
Kinematics Simulation ◽  
Simulation Based ◽  
Calculation Results ◽  
Simulation Results ◽  
Dynamics Simulations

The engine model with 4 cylinders is built by SolidWorks, the kinematics and dynamics simulations of the engine virtual prototype are done by COSMOSMotion, the results of kinematics simulation are checked, there are very small errors between the simulation results and the calculation results according to formulas. The mainly results of dynamics simulation are given. The simulation result consists with the parameters of the engine.

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